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Guidelines for Developing Spacecraft Structural Requirements: A Thermal and Environmental PerspectiveSpacecraft are typically designed with a primary focus on weight in order to meet launch vehicle performance parameters. However, for pressurized and/or man-rated spacecraft, it is also necessary to have an understanding of the vehicle operating environments to properly size the pressure vessel. Proper sizing of the pressure vessel requires an understanding of the space vehicle's life cycle and compares the physical design optimization (weight and launch "cost") to downstream operational complexity and total life cycle cost. This paper will provide an overview of some major environmental design drivers and provide examples for calculating the optimal design pressure versus a selected set of design parameters related to thermal and environmental perspectives. In addition, this paper will provide a generic set of cracking pressures for both positive and negative pressure relief valves that encompasses worst case environmental effects for a variety of launch / landing sites. Finally, several examples are included to highlight pressure relief set points and vehicle weight impacts for a selected set of orbital missions.
Document ID
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Holladay, Jon
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Day, Greg
(Boeing Co. Huntsville, AL, United States)
Gill, Larry
(Carleton Technologies, Inc. Orchard Park, NY, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2004
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
SAE Paper 2004-01-2284
Meeting Information
Meeting: 34th International Conference on Environmental Systems (ICES)
Location: Colorado Springs, CO
Country: United States
Start Date: July 19, 2004
End Date: July 22, 2004
Distribution Limits
Public Use Permitted.
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